Development and on-orbit verification of bipropellant accurate attitude control 10 N rocket engine
-
摘要:
介绍了我国最新一代精确冲量10 N火箭发动机及其关键部件研制与在轨验证。通过对地面验证试验的结果分析表明：该发动机真空比冲可达295 s，最小脉冲冲量优于30 mN·s，最小工作脉宽可达6 ms，累计点火寿命可达68.7 h，累计脉冲循环寿命不低于75万次，发动机可靠性得到了充分验证，并经实践二十卫星在轨成功飞行验证。该发动机的顺利研制是我国高性能双组元火箭发动机研制历史上一个重要的里程碑，标志着我国双组元火箭发动机整体技术达到了国际先进水平，具有广泛的社会和经济效益。
Abstract:The development and on-orbit verification of the latest accurate attitude control 10 N rocket engine in China were introduced. The analysis of ground hot tests showed that the vacuum-specific impulse of the engine reached 295 s. The minimum impulse was better than 30 mN·s, with a minimum working pulse width of 6 ms, a cumulative ignition life of 68.7 h, and a cumulative pulse cycle life of more than 750 000. The engine’s reliability was fully verified and successfully demonstrated through the SJ-20 satellite in orbital tests. The development of this engine marked an essential milestone in the development history of high-performance bipropellant attitude control engines in China, indicating that the overall technology of the bipropellant attitude control engines in China has reached the advanced international level and generated extensive social and economic benefits.
-
图 1 Astrium公司第二代双组元10 N火箭发动机（S10-18）示意图
Figure 1. The second generation bipropellant 10 N rocket engine （S10-18） of the Astrium company
图 2 双组元精确冲量10 N火箭发动机实物
Figure 2. Bipropellant accurate attitude control 10 N rocket engine
图 3 精确冲量10 N发动机各功能组件构成
Figure 3. Composition of the accurate attitude control 10 N rocket engine
图 5 发动机推力室实物和铌钨合金高温抗氧化涂层典型分层结构
Figure 5. Combustion chamber of the engine and Typical layered structure of high temperature oxidation resistance coating
图 6 发动机地面性能热试车验证结果
Figure 6. Verification results of the engine in the ground hot test
图 7 发动机热试车时温度测点分布示意图
Figure 7. Temperature measurement point distribution of the engine in the ground hot test
图 8 发动机在长稳态800 s点火时各测点温度变化示意图
Figure 8. Engine temperature changes during long-term steady state ignition for 800 s
图 9 发动机在典型脉冲工况点火时各测点温度变化示意图
Figure 9. Temperature changes during ignition of the engine under typical pulse conditions
图 10 发动机在小脉冲工况下脉冲冲量和平均比冲与脉冲宽度变化趋势
Figure 10. Variation trend of pulse impulse, average specific impulse, and pulse under small pulse operating conditions for the engines
图 11 发动机变入口压力工况性能
Figure 11. Engine performance under variable inlet pressure conditions
图 13 发动机的典型在轨工作温度曲线
Figure 13. Typical temperature curve of the engine on satellite’s orbital operating
表 1 精确冲量10 N火箭发动机主要技术指标
Table 1. Main specifications of accurate attitude control 10 N rocket engine
技术指标名称 指标要求 额定真空推力/N（20 ℃） 10×（（1±5）%） 真空比冲/ （N·s/kg） （≥290 s） ≥ 2842 混合比（20 ℃） 1.65×（（1±2）%） 最小脉冲冲量/（mN·s）（3σ，（1 ± 20）% ） ≤30 额定入口压力/MPa 1.6 一次最长连续点火时间/h ≥2 最长累计连续点火时间/h ≥22 发动机脉冲循环寿命/万次 ≥50 外漏率/10−4 （Pa·L/s） ≤1 内漏率/10−3 （Pa·L/s） ≤1 电磁阀开关响应时间（有载）/ms ≤5 电磁阀功耗/W（28 V DC，氧燃两阀并联驱动） ≤ 20 整机质量/kg 0.45±0.02 在轨使用寿命/年 16～20 
下载: 导出CSV
表 2 精确冲量10 N火箭发动机寿命验证情况
Table 2. Life verification status of accurate attitude control 10 N rocket engine
发动机
序号累计稳态
点火时间/h脉冲循环
点火次数/万次累计点火
总时长/h1 33 33 2 75 16.7 3 33 33 4 75 16.7 5 52 75 68.7 6 75 16.7 7 33 33 8 75 16.7
下载: 导出CSV
表 3 精确冲量10 N火箭发动机在轨累计点火时间统计
Table 3. On-orbit cumulative ignition time statistics of accurate attitude control 10 N rocket engine
星上位置 发动机代号 累计点火时间/s 1A 15 8759 2A 14 8970 3A 18 9621 4A 05 6838 5A 29 8464 6A 19 9124 7A 04 1230 8A 28 1230 1B 03 1701 2B 16 1699 3B 02 1683 4B 13 1671 5B 27 8464 6B 10 9124 7B 12 2 008 8B 21 2 008
下载: 导出CSV
表 4 发动机动量轮卸载效率统计表
Table 4. Efficiency of engine during the momentum wheel unloading process
动量轮
卸载日期发动机卸载
角动量/（N·ms）动量轮角动量
变化/（N·ms）效率/% 2020-02-04 2.769 2.713 98.00 2020-06-10 2.769 2.675 96.61 2021-04-09 2.769 2.681 96.84 2021-07-22 0.923 0.907 98.27 2022-04-08 0.923 0.893 96.75
下载: 导出CSV
-
[1] 李亚裕. 液体推进剂[M]. 北京: 中国宇航出版社, 2011: 14-34. [2] 魏延明. 国外卫星推进技术发展现状与未来20年发展趋势[J]. 航天制造技术, 2011(2): 7-12. WEI Yanming. Current situation and developing direction of foreign satellite propulsion technology in the next 20 years[J]. Aerospace Manufacturing Technology, 2011(2): 7-12. (in ChineseWEI Yanming. Current situation and developing direction of foreign satellite propulsion technology in the next 20 years[J]. Aerospace Manufacturing Technology, 2011(2): 7-12. (in Chinese) [3] SCHULTE G, GOTZIG U, HORCH A, et al. Further improvements and qualification status of astriums 10 N bipropellant thruster family: AIAA 2003-4776 [R]. Huntsville, US: 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2003. [4] 李果, 刘良栋, 张洪华. 航天器控制若干技术问题的新进展[J]. 空间控制技术与应用, 2008, 34(1): 14-19. LI Guo, LIU Liangdong, ZHANG Honghua. Recent progress of several technical problems with spacecraft control[J]. Aerospace Control and Application, 2008, 34(1): 14-19. (in ChineseLI Guo, LIU Liangdong, ZHANG Honghua. Recent progress of several technical problems with spacecraft control[J]. Aerospace Control and Application, 2008, 34(1): 14-19. (in Chinese) [5] 官长斌, 毛晓芳, 王平, 等. 基于能量回收原理的高速电磁阀仿真与试验研究[J]. 推进技术, 2020, 41(3): 668-674. GUAN Changbin, MAO Xiaofang, WANG Ping, et al. Simulation and experiment on high-speed solenoid valve based on energy recovery principle[J]. Journal of Propulsion Technology, 2020, 41(3): 668-674. (in ChineseGUAN Changbin, MAO Xiaofang, WANG Ping, et al. Simulation and experiment on high-speed solenoid valve based on energy recovery principle[J]. Journal of Propulsion Technology, 2020, 41(3): 668-674. (in Chinese) [6] 汪凤山, 毛晓芳, 虞育松, 等. 双组元离心式喷注器雾化性能的大涡模拟数值研究[J]. 空间控制技术与应用, 2012, 38(6): 13-17. WANG Fengshan, MAO Xiaofang, YU Yusong, et al. Numerical LES study of spray performance in a bi-propellant coaxial centrifugal injector[J]. Aerospace Control and Application, 2012, 38(6): 13-17. (in ChineseWANG Fengshan, MAO Xiaofang, YU Yusong, et al. Numerical LES study of spray performance in a bi-propellant coaxial centrifugal injector[J]. Aerospace Control and Application, 2012, 38(6): 13-17. (in Chinese) [7] JENG S M, JOG M A, BENJAMIN M A. Computational and experimental study of liquid sheet emanating from simple fuel nozzle: AIAA 97-0796[R]. Reno, US: Aerospace Sciences Meeting & Exhibit, 1997. [8] SARIC W S, MARSHALL B W. An experimental investigation of the stability of a thin liquid layer adjacent to a supersonic stream[J]. AIAA Journal, 1971, 9(8): 1546-1553. doi: 10.2514/3.49958 [9] GOTZIG U, SCHULTE G, SOWA A. New generation 10 N bipropellant MMH/NTO thruster with double seat valve: AIAA 99-2594[R]. Los Angeles, US: AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1999. [10] 王平, 汪凤山, 胡羽, 等. 离心喷嘴脉冲工作动态特性实验研究[J]. 推进技术, 2022, 43(9): 210196. WANG Ping, WANG Fengshan, HU Yu, et al. Experimental study on dynamic characteristics of swirl injector working in pulse mode[J]. Journal of Propulsion Technology, 2022, 43(9): 210196. (in ChineseWANG Ping, WANG Fengshan, HU Yu, et al. Experimental study on dynamic characteristics of swirl injector working in pulse mode[J]. Journal of Propulsion Technology, 2022, 43(9): 210196. (in Chinese) [11] 杨立军, 王向东, 富庆飞. 液体离心式喷嘴脉动流量测量方法[J]. 推进技术, 2008, 29(6): 721-725. YANG Lijun, WANG Xiangdong, FU Qingfei. Conductance measurement method of pulsing flow in liquid swirl injector[J]. Journal of Propulsion Technology, 2008, 29(6): 721-725. (in Chinese doi: 10.3321/j.issn:1001-4055.2008.06.017YANG Lijun, WANG Xiangdong, FU Qingfei. Conductance measurement method of pulsing flow in liquid swirl injector[J]. Journal of Propulsion Technology, 2008, 29(6): 721-725. (in Chinese) doi: 10.3321/j.issn:1001-4055.2008.06.017 [12] FU Q F, YANG L J, QU Y Y. Measurement of annular liquid film thickness in an open-end swirl injector[J]. Aerospace Science and Technology, 201l, 15(2): 117-124. [13] AHN B, ISMAILOV M, HEISTER S. Experimental study swirl injector dynamic response using a hydromechanical pulsator[J]. Journal of Propulsion and Power, 2012, 28(3): 585-595. doi: 10.2514/1.B34261 [14] 符鹏飞, 侯凌云, 巴延涛, 等. 小推力双组元火箭发动机中壁面液膜数值模拟[J]. 燃烧科学与技术, 2017, 23(4): 299-304. FU Pengfei, HOU Lingyun, BA Yantao, et al. Numerical simulation of wall liquid film in small bipropellant rocket engine[J]. Journal of Combustion Science and Technology, 2017, 23(4): 299-304. (in ChineseFU Pengfei, HOU Lingyun, BA Yantao, et al. Numerical simulation of wall liquid film in small bipropellant rocket engine[J]. Journal of Combustion Science and Technology, 2017, 23(4): 299-304. (in Chinese) [15] INAMURA T, AMAGASAKI S, YANAOKA H. Thickness of liquid film formed by impinging jets on a concave wall[J]. Journal of Propulsion and Power, 2007, 23(3): 612-617. doi: 10.2514/1.27691 [16] 曹顺, 汪凤山, 陈健. 双组元推力器雾化燃烧过程数值模拟及液膜冷却作用分析[J]. 空间控制技术与应用, 2012, 38(2): 58-62. CAO Shun, WANG Fengshan, CHEN Jian. Numerical simulation of working process in chamber of bipropellant thruster and analysis of film-cooling effect[J]. Aerospace Control and Application, 2012, 38(2): 58-62. (in ChineseCAO Shun, WANG Fengshan, CHEN Jian. Numerical simulation of working process in chamber of bipropellant thruster and analysis of film-cooling effect[J]. Aerospace Control and Application, 2012, 38(2): 58-62. (in Chinese) [17] 曹顺, 陈健, 汪凤山. 双组元推力器喷注角度对液膜分布的影响分析[J]. 空间控制技术与应用, 2012, 38(6): 45-49. CAO Shun, CHEN Jian, WANG Fengshan. The influence of bi-propellant-thruster injection angles on liquid-film distribution[J]. Aerospace Control and Application, 2012, 38(6): 45-49. (in ChineseCAO Shun, CHEN Jian, WANG Fengshan. The influence of bi-propellant-thruster injection angles on liquid-film distribution[J]. Aerospace Control and Application, 2012, 38(6): 45-49. (in Chinese) [18] 张榛, 虞育松, 侯凌云, 等. 喷雾液滴与涂层壁面作用的机理性试验及其影响研究[J]. 推进技术, 2019, 40(7): 1560-1567. ZHANG Zhen, YU Yusong, HOU Lingyun, et al. Experimental study on mechanism of spray droplet interaction with coating wall and its influence[J]. Journal of Propulsion Technology, 2019, 40(7): 1560-1567. (in ChineseZHANG Zhen, YU Yusong, HOU Lingyun, et al. Experimental study on mechanism of spray droplet interaction with coating wall and its influence[J]. Journal of Propulsion Technology, 2019, 40(7): 1560-1567. (in Chinese) [19] 巴延涛, 侯凌云, 毛晓芳, 等. 甲基肼/四氧化二氮反应化学动力学模型构建及分析[J]. 物理化学学报, 2014, 30(6): 1042-1048. BA Yantao, HOU Lingyun, MAO Xiaofang, et al. Construction and analysis of a chemical kinetic model for monomethylhydrazine/nitrogen tetroxide reactions[J]. Acta Physico-Chimica Sinica, 2014, 30(6): 1042-1048. (in Chinese doi: 10.3866/PKU.WHXB201404093BA Yantao, HOU Lingyun, MAO Xiaofang, et al. Construction and analysis of a chemical kinetic model for monomethylhydrazine/nitrogen tetroxide reactions[J]. Acta Physico-Chimica Sinica, 2014, 30(6): 1042-1048. (in Chinese) doi: 10.3866/PKU.WHXB201404093 [20] 毛晓芳, 汪凤山, 杨晓红, 等. 小推力双组元姿控发动机性能研究[J]. 推进技术, 2012, 33(6): 987-990. MAO Xiaofang, WANG Fengshan, YANG Xiaohong, et al. Investigation on performance of small-thrust bi-propellant thruster for attitude control[J]. Journal of Propulsion Technology, 2012, 33(6): 987-990. (in ChineseMAO Xiaofang, WANG Fengshan, YANG Xiaohong, et al. Investigation on performance of small-thrust bi-propellant thruster for attitude control[J]. Journal of Propulsion Technology, 2012, 33(6): 987-990. (in Chinese) [21] CAI Kun, ZHANG Zhen, WANG Na, et al. Effect of the MoSi2 coating on operational reliability of bipropellant rocket engine[J]. E3S Web of Conferences, 2021, 260: 03003. doi: 10.1051/e3sconf/202126003003 [22] 汪凤山, 姚兆普, 刘阳, 等. 甲基肼/四氧化二氮发动机脉冲工况仿真与试验研究[J]. 空间控制技术与应用, 2021, 47(4): 56-62. WANG Fengshan, YAO Zhaopu, LIU Yang, et al. Numerical and experimental analysis of pulse mode characteristics in a MMH/NTO rocket engine[J]. Aerospace Control and Application, 2021, 47(4): 56-62. (in ChineseWANG Fengshan, YAO Zhaopu, LIU Yang, et al. Numerical and experimental analysis of pulse mode characteristics in a MMH/NTO rocket engine[J]. Aerospace Control and Application, 2021, 47(4): 56-62. (in Chinese) [23] ZHANG Zhen, YU Yusong, CAI Kun, et al. Computational simulation study on the influence of spray/wall impact on the mixing characteristics of bipropellant centrifugal apogee engine[J]. Journal of Physics: Conference Series, 2020, 1624(2): 022054. doi: 10.1088/1742-6596/1624/2/022054 [24] 王娜, 李海庆, 徐方涛, 等. 双组元液体火箭发动机推力室材料研究进展[J]. 宇航材料工艺, 2019, 49(3): 1-8. WANG Na, LI Haiqing, XU Fangtao, et al. Recent development of advanced materials for liquid rocket thruster chambers[J]. Aerospace Materials & Technology, 2019, 49(3): 1-8. (in Chinese doi: 10.12044/j.issn.1007-2330.2019.03.001WANG Na, LI Haiqing, XU Fangtao, et al. Recent development of advanced materials for liquid rocket thruster chambers[J]. Aerospace Materials & Technology, 2019, 49(3): 1-8. (in Chinese) doi: 10.12044/j.issn.1007-2330.2019.03.001 [25] 张亚晨, 孟佳, 蔡坤, 等. 基于声发射技术的Si-Cr-Ti高温抗氧化涂层弯曲失效机理研究[J]. 无机材料学报, 2021, 36(11): 1185. ZHANG Yachen, MENG Jia, CAI Kun, et al. Bending failure mechanism study of Si-Cr-Ti high temperature oxidation resistance coating via acoustic emission technique[J]. Journal of Inorganic Materials, 2021, 36(11): 1185. (in Chinese doi: 10.15541/jim20210032ZHANG Yachen, MENG Jia, CAI Kun, et al. Bending failure mechanism study of Si-Cr-Ti high temperature oxidation resistance coating via acoustic emission technique[J]. Journal of Inorganic Materials, 2021, 36(11): 1185. (in Chinese) doi: 10.15541/jim20210032 -
点击查看大图
计量
- 文章访问数: 683
- HTML浏览量: 735
- PDF量: 43
- 被引次数: 0